Aeroplane



J. P. LANGFELDER mm 2%, W25,

AEROPLANE Filed May 22. 1922 3 SheeisT-Sh t l I N V EN TOR.

HG FEL DEB FLA JOHN

ATTORNEY April. 28 E925.

J. P. LANGFELDER -AERoPLAuE Filed May 22. 1922 :5 Sheets- Sheet s INVENTOR.

JZ/HH PLA N6 FEL DE/E,

BY a I Patented Apr. 28, 1925.

1,535,532 PATENT OFFICE.

JOHN P. LANGFELDER, OF JAMAICA, YORK, ASSIGNOR, BY MESNE ASSIGNMENTS, TO GURTISS AEROPLANE AND MOTOR COMPANY, INC., 015 GARDEN CITY, NEW YORK,

' A. CORPORATION 015 NEW YORK.

annornann.

Application filed May 22;

To all whom it may concern:

Be it known th t I, J oHN'P. LANornLonR, acitizen of the United States, reslding at ,Jamaica, in the county of Queens and State.

manner that, in an emergency, it is capable of being quickly released and shed clear of the machine.

A still further object of the invention is to provide a fuel tank support, which, when p retracted, holds the fuel tank firmly in place,

and which, when extended, guides the fuel tank in its initial movement to prevent it from subsequently fouling some other part of the machine. 7

Other objects and advantages of the invention will be hereinafter explained.

In the drawings I Figure 1 is a perspective view of an aeroplane fuselage, partly broken away, showing the relation of the motive fuel tank and its support;

Figure 2 is a side elevation of the fuel tank and its support showing the relative position of the parts thereof; the full lines indicating the position of the tank and the support when the latter is retracted and the fuel tankheld firmly in place, the dotted lines indicating the position of the support subsequent to its release;

Figure 3 is a fragmentary side elevation of aportion bftll'e rlease mechanism;

Figure-4 is an enlarged transverse vertical; sectional view better illustrating the relation of the fuel tank and its support;

' Figure 5 is a side elevation of a modified form of gas tank release; and

Figures 6, 7, and 8 are detail views of such modifications.

In the embodiment of the invention selected. for illustration, the aeroplane fuselage or body is designated in its entirety as 10. Said fuselage or body is preferably of the skeleton framework type and comprises longerons 11,

1922. Serial No. 562,618.

f selage struts 12, and suitable covering 13, he latter for a portion of its length on the under side of the skeleton framework being interrupted whereby space is provided for the fitting engagement therein of the motive fuel tank. The motive fuel tank, designated in its entirety as 14, is so shaped and constructed as to completely fill the space above referred to, that the continuity of the fuselage cover 13 is uninterrupted when said fuel tank is inplace. In other words, when the fuel tank is in place it may be said to actually form a composite part of the fuselage or body cover. Thus positioned, obviously it is-an easy matter to shed the fuel tank in an emergency.

The fuel-tank, instead ofbeing directly fastened to the skeleton framework of the body is held in place by a support 15 which is adapted to be extended and retracted according to whether or not it is desired that the fuel tank be released. Normally the support 15 occupies a position indicated by the full lines of Figure 2. Thus positioned, the fuel tank 1 1 by reason of its engagement with the support, is held firmly in place close up against the under side of the fuselage skeleton framework, suitable release mechanism being provided for this purpose.

The support 15 comprises guide rails 16 1-" within which rollers 17 are free to rotate'.,,

These rollers 17 are carried by fittings 18 directly fastened to the fuel tank. When the fuel'tank is released the rollers 17 are free to move alon the rails 16 that the initial movement of the tank, during a shedding operation, may be properly'controlled. The guide 'rails 16 are at all times held in parallelism by links 19 pivoted respectively to the fuselage and to the rails.'. Preferably the forward pair of links 19 is shorter than the rear pair, that the rails 16, when the support is extended, will assume an inclined position, the inclination beink directed downwardly toward the rear. Thus positioned, the fuel 9 saidfigure, in which latter position, the fuel 2 messes fittings 20 and consequently the support 15 stresses due to the weight of the tank. To

and fuel tank 14 in place; insure a positive movement of the tank away In Figures 3 and 4 the release mechanism from the fuselage during a release operais illustrated in detail. Preferably such tion, a push rod 37 may be provided, said mechanism includes a lever 21 pivoted as at push rod at one end being fastened to the 22 and a trip 23 pivoted intermediately of cross arm 29 of the operating lever and at its ends as at 24 and at one end fastened as its opposite end movable into engagement at 25 to a release bar 26. Where the release with the top surface of the tank. mechanism is duplicated at opposite sides of the fuselage and at intervals throughout trated in Figures 5 to 8 inclusive, it will be the length of the fuel tanksupport, the renoted that the operating mechanism whereby lease bar 26 is of a construction such that the tank is released is substanita-lly the same the total number of trips 23 will be oper as the operating mechanism above described.

Referring next to the modifications illusated simultaneously. In the present inven- The fuel tank, however, instead of being tion such duplication of the release mechamade as a single tank. is madeup of sepanism is provided. To actuate the release rate tank sections. Collectively the tank bars 26,,an operating lever 27 is provided. sections, when held in place, .are of substan- Such lever is preferably conveniently located tially the same size and shape as the unit in proximity to the pilots seat. It is tank, though when released, are adapted to pivoted at one end as indicated at 28 and be released'and shed in a somewhat different provided with a cross arm 29. To the formanner, the forward tank section being movward end of the cross arm 29 a wire cable able initially and the rear tank section fol- 30 is fastened, said cable being passed over lowing. In saidmodification, no guide rails guide pulleys 31 and carried to the separate are provided. There is provided instead, release bars on the opposite sides of the for the forward tank section 40, levers 41, fuselage. In addition to providing a means said levers-being pivoted to the tank 40 at for simultaneously actuating both release one 'end and to the rear tank section 42 at bars 26, the cable 30 by reason of its reartheir opposite ends as indicated at 43. Each ward extension as indicated at 32, provides v of said'levers 41 adjacent to the pivots 43'is also an operating means for a knife 33 which provided with an eccentric extension 44 is adapted to cut the fuel feed lines 34 leadwhich in the retracted position ofth'e levers 'ing from the tank 14 to the motor (not 41 are adapted to engage and overhang pin shown). In operation, the knife 33 isopersupports 45 fastened to the longerons'of the ated slightly in advance of the release mechfuselage. As the tank sections 40 and 42 are anism that the fuel feed lines may be cut released, the release mechanism being prefbefore the fuel tank is, fully released. As erably the same as in the preferred form of the release bars 26 are moved forwardly my invention, the tank section 40 first moves through the operation of the lever 27, obvifrom the full line position indicated in Figously the total number of trips 23 are simulure 5 to the dotted line position indicated taneously moved about their respective in said figure, such'movement continuing in pivots 24 to simultaneously release the total the direction indicated until the eccentric number of levers 21, and since the levers 21 extensions 44 of the levers 41 are free from by reason of their engagement with the fitengagement with the pin supports 45. t1ngs 20 hold the support 15 inits retracted When entirely free from such engagement, pos1t1on obvlously, the moment the levers 21- obviously both tanks are free to fall,-the one are released, the weight of the fuel tank will cause the support 15 to drop from the position indicated by the full lines in Figure 2 to the position indicated by the dotted lines in tank 14 is free" to move" bodily rearwardly toward the lower end of the inclined rails 16. To hold the support 15 in place subsequent to its release, a stop wire 35 is rovided. Preferably the release mechanism,

in each instance, is made as an'integral part I .of such ordlnary fuselage fittings as are usually provided at the point of. intersection of the fuselage struts 12. If desired, abutments 36' may bra-provided at o posite sides of the fuel tank to ear against t e longerons of the. fuselage when the tank '14 is held in place. These abutments 36 tendto prevent undue vibration of the fuel tank and at the same time better distributethe inertia slightly in advance of the other.

While I have described myinvention in to cover all such modifications and changes.

What I claim is mechanism operable to release the support, and a. fuel tank movable with and with respect to the support upon its'release.

2.: In an aeroplane, a combined guide and support, mechanism operable to release the 1. In an aeroplane, a movable support,

combined guide and support, and a fuel tank carried by and movable with and with upon its release.

respect to the combined guide and support emma 3. In an aeroplane, a fuselage, a support the fuel tank from a retracted position close up against the body of the machine to an extended position therebeneath, means for holding the support in its retracted position, mechanism operable to release the support and a guide means for'the fuel tank for directing its movement after the support has been released.

5. ln an aeroplane, a support for a fuel tank movable from a retracted position withinv the body of the aeroplane to an extended position therebeneath, a fuel tank carried by and movable with and with respect to said support, and mechanism operable to release said support.

6. lln an aeroplane, a support for a fuel tank movable from a retracted position within the body of the aeroplane to an extended position therebeneath, a fuel tank carried by and movable with the support from its retracted to its extended position and movable with respect to said support when the latter is fully extended, and

support, and when said support is in its fully extended osition, movable along said guides until it l the fuel tank) is shed clear of the support and also the machine, and

mechanism operable to release the support.

8. In an aeroplane, a support for a fuel tank movable from a retracted position close up against the under surface of the body of the aeroplane to an extended position therebeneath, a fuel tank movable with the support when the latter is released until it (the fuel tank) is entirely clear of the body of the machine, said fuel tank subsequent to such movement being movable relatlvely to the support in order that it may be shed clear thereof as well as of the machine, and mechanism operable to release the'support. 9. In an aeroplane, a support for a fuel tank movable from a retracted position within the body of the aeroplane to an extended position 'therebeneath, means associated with the support to limit its falling movement when released, a fuel tank carried by and movable with the support and also movable with respect to said support when the latter shall have attained lowermost position, and mechanism operable to release the support. v

10. lln an aeroplane, a support for a fuel tank normally carried'close up against the under surface of the body of the machine, mechanism operable to release the support, means associated with said support to limit its movement when released, and a fuel tank carried by and movable with the support throughout its limited movement and with respect thereto when its limit of movement shall have been reached.

in testimony whereof ll hereunto a my signature.

Jenn r. nanernnnnn. 

